专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

71. 发明公开

EP2855878A1 COMPRESSOR TIP CLEARANCE MANAGEMENT FOR A GAS TURBINE ENGINE 有权转让
标题翻译：燃气涡轮发动机压气机管口间隙管理
公开(公告)号：EP2855878A1
公开(公告)日：2015-04-08
申请号：EP13800008.8
申请日：2013-05-17
申请人： United Technologies Corporation
发明人： DONG, Yuan , BRILLIANT, Lisa I. , CARMINATI, Daniel , SIRICA, Steven J.
IPC分类号： F02C7/00 , F02C7/057 , F02C9/00 , F02C3/00
CPC分类号： F01D11/08 , F02C9/20 , F04D27/004 , F04D27/0246 , F04D27/0261 , F04D29/164 , F04D29/563
摘要： A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.
摘要翻译：压缩机叶尖间隙管理系统包括具有低压压缩机的压缩机部分和布置在低压压缩机下游的高压压缩机。可变定子叶片布置在高压压缩机的上游。可变定子叶片连接到致动器，并且控制器与致动器连通。控制器构造成响应于高压压缩机间隙状况向致动器提供命令以移动可变定子叶片。高压压缩机转子速度改变，并且高压压缩机间隙条件改变为期望的间隙。

72. 发明授权

EP2642092B1 Method for operating a combined cycle power plant and plant to carry out such a method 有权转让
标题翻译：用于操作联合循环发电设备和植物用于执行这样的方法的方法
公开(公告)号：EP2642092B1
公开(公告)日：2014-10-08
申请号：EP13158572.1
申请日：2013-03-11
申请人： Alstom Technology Ltd
发明人： Brighenti, Andrea , Lilley, Darrel Shayne , Franitza, Karsten , Nemet, Anton
IPC分类号： F01K23/10 , F02C9/20 , F02C3/34 , F02C6/18 , F02C7/141 , F01K13/02 , F02C7/057 , F02C7/08 , F01K21/00
CPC分类号： F01K21/00 , F01K23/101 , F02C6/18 , F05D2270/083 , F05D2270/0831 , F05D2270/303 , Y02E20/14 , Y02E20/16

73. 发明公开

EP2660442A3 Integrated thermal protection and leakage reduction in a supersonic air intake system 审中-公开
标题翻译：集成的热保护和减少渗漏的超音速进气系统
公开(公告)号：EP2660442A3
公开(公告)日：2014-09-24
申请号：EP13166256.1
申请日：2013-05-02
申请人： Lockheed Martin Corporation
发明人： Leland, Brad C. , Tworek, Andrew J. , Cho, Chan
IPC分类号： F02C7/057 , B64C21/06 , F02C9/18 , F02K1/30 , F02C7/141 , F02K7/10 , B64D33/02
CPC分类号： B64D33/02 , B64D2033/026 , F02C7/057 , F02C7/141 , F02C9/18 , F02K1/30 , F02K7/10 , F05D2220/80 , F05D2270/17 , Y02T50/671 , Y02T50/675 , Y10T137/0536
摘要： An air intake system suitable for a supersonic vehicle is disclosed. The system includes a channel comprising an inlet and a side wall and a plenum coupled to the side wall. The plenum is configured to accept a flow of coolant. In certain embodiments, the coolant is the waste coolant from an on-board electronics cooling system. The system also includes a porous region in the side wall configured to allow a flow of bleed air from the channel through the porous region of the side wall into the plenum so as to aid the transition to supersonic flow. In certain embodiments, the flow of the bleed air is reduced at supersonic speeds by pressurization of the plenum with the coolant.

74. 发明授权

EP1992810B1 Variable contraction ratio nacelle assembly for a gas turbine engine 有权转让
标题翻译：缆车与用于飞机发动机的可变几何形状和操作方法对应
公开(公告)号：EP1992810B1
公开(公告)日：2014-05-28
申请号：EP08251743.4
申请日：2008-05-19
申请人： United Technologies Corporation
发明人： Jain, Ashok K. , Winter, Michael
IPC分类号： F02K3/06 , F02C7/042 , F02C7/057
CPC分类号： F02K3/06 , F02C7/042 , F02C7/057 , F05D2300/505 , Y02T50/671

75. 发明公开

EP2728143A2 Inlet bleed heat system with integrated air knife/siliencer panels 审中-公开
标题翻译： Einlassentlüftungsheizsystemmit integrierten Luftmesser-Schalldämpferplatten
公开(公告)号：EP2728143A2
公开(公告)日：2014-05-07
申请号：EP13191626.4
申请日：2013-11-05
申请人： General Electric Company
发明人： Hao, Yongjiang , Byrd, Douglas Scott , Zhang, Hua , Kippel, Bradly Aaron , Zhang, Jianmin
IPC分类号： F02C7/045 , F02C7/057
CPC分类号： F01D25/08 , F01D25/10 , F02C6/06 , F02C7/04 , F02C7/045 , F02C7/057 , F05D2260/96
摘要： The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may include an air knife (160) and a silencer panel (230). The air knife may include a compressor bleed air port (170) in communication with the flow of bleed air and a discharge gap (190) to discharge the flow of bleed air into the flow of incoming air. The air knife may and the silencer panel may form an integrated air knife/silencer panel.
摘要翻译：本申请提供了一种入口放气加热系统，用于将进气流输送到燃气涡轮发动机的压缩机中。入口放气加热系统可以包括气刀（160）和消音器面板（230）。气刀可以包括与排出气流连通的压缩机排气口（170）和排放间隙（190），以将排出的空气排放到进入的空气流中。气刀可以和消声器面板形成一体的气刀/消声器面板。

76. 发明公开

EP2256299A3 Deflector for a gas turbine strut and vane assembly 有权
标题翻译：用于燃气轮机支柱和叶片组件的导流板
公开(公告)号：EP2256299A3
公开(公告)日：2014-04-09
申请号：EP10250678.9
申请日：2010-03-31
申请人： Pratt & Whitney Canada Corp.
发明人： Durocher, Eric , Tsifourdaris, Panagiota , Sleiman, Mohamad
IPC分类号： F01D9/06 , F01D25/14 , F01D25/16 , F01D25/24 , F01D25/28 , F01D5/14 , F01D9/02 , F01D9/04 , F01D17/14 , F02C7/057 , F02C9/22 , F04D29/54
CPC分类号： F01D25/14 , F01D5/142 , F01D5/143 , F01D5/146 , F01D9/02 , F01D9/041 , F01D9/06 , F01D17/143 , F01D25/16 , F01D25/24 , F01D25/28 , F02C7/057 , F02C9/22 , F04D29/544
摘要： A gas turbine engine is provided having an annular duct (136) having an inner duct wall (116) and an outer duct wall (114). At least one strut (118) extends between the inner duct wall (116) and the outer duct wall (114). The strut (118) has an aerodynamic shape. At least one vane (134) is located circumferentially adjacent the strut (118) and axially behind a leading edge (112) of the strut (118), and an aerodynamic deflector (150) is located circumferentially between each strut (118) and each vane (134). The aerodynamic deflector (150) may positioned axially upstream of a flow separation point which would otherwise be caused by the strut (118).
摘要翻译：提供了一种燃气涡轮发动机，其具有具有内部管道壁（116）和外部管道壁（114）的环形管道（136）。至少一个支柱（118）在内管道壁（116）和外管道壁（114）之间延伸。支柱（118）具有空气动力学形状。至少一个叶片（134）位于支撑件（118）的周向上并且在支撑件（118）的前缘（112）的轴向后方定位，并且空气动力学偏转器（150）周向地位于每个支撑件（118）与每个支撑件叶片（134）。空气动力学偏转器（150）可以轴向定位在否则将由支柱（118）引起的流动分离点的上游。

77. 发明公开

EP2620617A2 Combustion turbine inlet anti-icing resistive heating system 审中-公开
标题翻译： FrostbeständigesGasturbineneinlassheizsystem
公开(公告)号：EP2620617A2
公开(公告)日：2013-07-31
申请号：EP13152743.4
申请日：2013-01-25
申请人： General Electric Company
发明人： Scipio, Alston Ilford , Ekanayake, Sanji , Vu, Huong Van , Motakef, Abbas
IPC分类号： F02C7/047 , F02C7/052 , F02C7/055 , F02C7/057
CPC分类号： F02C7/047 , F02C7/052 , F02C7/055 , F02C7/057 , F05D2250/51
摘要： A resistive heating system for a combustion turbine susceptible to inlet air filter house component (42) and compressor icing includes a plurality of heating panels (bundles) (48) arranged in a substantially-planar array (46, 47), adapted to be located on or adjacent to the turbine's inlet air filter house (42). Each heating panel (48) is provided with one or more electrically-resistive heating elements (50); and a controller for selectively activating the resistive heating elements (50) on each of the plurality of heating panels (48).
摘要翻译：用于对入口空气过滤器室部件（42）和压缩机结冰敏感的燃烧涡轮的电阻加热系统包括布置在基本上平面的阵列（46,47）中的多个加热板（束）（48），适于定位在涡轮机的入口空气过滤器室（42）上或附近。每个加热板（48）设置有一个或多个电阻加热元件（50）; 以及用于选择性地激活多个加热板（48）中的每一个上的电阻加热元件（50）的控制器。

78. 发明公开

EP2607657A2 Active flow control intake for a gas turbine engine 审中-公开
标题翻译： Gasturbinen-Lufteinlass mit aktiverStrömungssteuerung
公开(公告)号：EP2607657A2
公开(公告)日：2013-06-26
申请号：EP12196985.1
申请日：2012-12-13
申请人： Rolls-Royce plc
发明人： Richardson, Giles Anthony , Sheaf, Christopher
IPC分类号： F02C7/057 , F02C7/047 , F02C7/045
CPC分类号： F01D17/00 , F02C7/045 , F02C7/047 , F02C7/057 , Y02T50/671
摘要： Intakes (11) of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement (30) for an intake (11) comprises a compressed gas supply pipe (31,33) , a valve arrangement (32), a controller (34), and a compressed gas distribution pipe(50). The supply pipe (31,33) is fluidly connects between a compressed gas source and the valve arrangement (32). The distribution pipe fluidly (50) connects between the valve arrangement (32) and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan.
摘要翻译：燃气涡轮发动机的进气（11）经受交叉风和高入射横流，这可能影响到推进风扇的空气的稳定性。用于进气口（11）的主动流量控制装置（30）包括压缩气体供给管（31,33），阀装置（32），控制器（34）和压缩气体分配管（50）。供给管（31,33）在压缩气体源和阀装置（32）之间流体连通。流体配管（50）连接在阀装置（32）和进气表面之间，用于向其供应压缩气体。主动流量控制装置可操作以将压缩气体供应到进气表面，以防止从入口表面分离通过进气口的主空气流，从而保持进气流向风扇的稳定性。

79. 发明公开

EP2592236A2 Bleed system for heating the inlet air of a compressor 有权转让
标题翻译： Zapfluftsystem zurErwärmungder Einlassluft eines Verdichters
公开(公告)号：EP2592236A2
公开(公告)日：2013-05-15
申请号：EP12191433.7
申请日：2012-11-06
申请人： General Electric Company
发明人： Ponyavin, Valery Ivanovich , Zhang, Hua
IPC分类号： F01D17/00 , F02C7/045 , F02C7/047 , F02C7/057
摘要： An embodiment of the present invention takes the form of an IBH system (95) has a single conduit (107), which is positioned close to a downstream end of a silencer section (90). This arrangement may reduce the overall pressure drop associated with the inlet system (55). This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.
摘要翻译：本发明的实施例采用IBH系统（95）的形式，其具有靠近消声器部分（90）的下游端定位的单个导管（107）。这种布置可以减少与入口系统（55）相关联的总压降。这种布置还可以促进较冷的环境空气和较热的加热空气之间的基本均匀的混合。

80. 发明公开

EP2034159A3 Active flow control for nacelle air intake 有权转让
标题翻译：进气口用于与主动流动控制喷气发动机
公开(公告)号：EP2034159A3
公开(公告)日：2012-01-04
申请号：EP08252911.6
申请日：2008-09-02
申请人： United Technologies Corporation
发明人： Hurwitz, Wayne , Ochs, Stuart S.
IPC分类号： F02C7/057 , B64C21/06 , B64D29/00 , F15D1/12 , F01D17/02
CPC分类号： F02C7/057 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D17/02 , F05D2270/301 , F05D2270/44 , F05D2270/62
摘要： The disclosed turbine engine (10) includes a fan nacelle (34) surrounding a fan (20) and including an inlet (35) arranged upstream from the fan (20). The inlet (35) includes an inlet surface (74) having a boundary layer flow. A flow control actuator (54) is in fluid communication with the inlet surface (74). A boundary layer sensing device (52) is associated with the inlet surface (74) for detecting a boundary layer condition at the inlet surface (74). A controller (50) is in communication with the flow control actuator (54) and the boundary layer sensing device (52). The controller (50) is programmed to command the flow control actuator (54) in response to the boundary layer sensing device (52) detecting an undesired boundary layer condition. In this manner, the flow control actuator (54) generates a desired boundary layer condition.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式